US9200808B2 - System for supplying fuel to a late-lean fuel injector of a combustor - Google Patents

System for supplying fuel to a late-lean fuel injector of a combustor Download PDF

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Publication number
US9200808B2
US9200808B2 US13/457,726 US201213457726A US9200808B2 US 9200808 B2 US9200808 B2 US 9200808B2 US 201213457726 A US201213457726 A US 201213457726A US 9200808 B2 US9200808 B2 US 9200808B2
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United States
Prior art keywords
liquid fuel
combustion chamber
baffle
passages
fuel plenum
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US13/457,726
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English (en)
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US20130283801A1 (en
Inventor
Bryan Wesley Romig
Lucas John Stoia
Patrick Benedict MELTON
Thomas Edward Johnson
Gregory Allen Boardman
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GE Vernova Infrastructure Technology LLC
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General Electric Co
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Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: MELTON, PATRICK BENEDICT, BOARDMAN, GREGORY ALLEN, Romig, Bryan Wesley, STOIA, LUCAS JOHN, JOHNSON, THOMAS EDWARD
Priority to US13/457,726 priority Critical patent/US9200808B2/en
Priority to EP13165222.4A priority patent/EP2657611B1/en
Priority to JP2013091859A priority patent/JP6203528B2/ja
Priority to RU2013119328A priority patent/RU2618765C2/ru
Priority to CN201310149399.5A priority patent/CN103375816B/zh
Publication of US20130283801A1 publication Critical patent/US20130283801A1/en
Publication of US9200808B2 publication Critical patent/US9200808B2/en
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Assigned to GE INFRASTRUCTURE TECHNOLOGY LLC reassignment GE INFRASTRUCTURE TECHNOLOGY LLC ASSIGNMENT OF ASSIGNOR'S INTEREST Assignors: GENERAL ELECTRIC COMPANY
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/36—Supply of different fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems

Definitions

  • the present invention generally involves a system for supplying fuel to a combustor.
  • one or more injectors circumferentially arranged around the combustor may supply a lean mixture of liquid fuel, gaseous fuel, and/or working fluid to the combustor.
  • Combustors are commonly used in industrial and power generation operations to ignite fuel to produce combustion gases having a high temperature and pressure.
  • gas turbines typically include one or more combustors to generate power or thrust.
  • a typical gas turbine used to generate electrical power includes an axial compressor at the front, one or more combustors around the middle, and a turbine at the rear.
  • Ambient air may be supplied to the compressor, and rotating blades and stationary vanes in the compressor progressively impart kinetic energy to the working fluid (air) to produce a compressed working fluid at a highly energized state.
  • the compressed working fluid exits the compressor and flows through one or more nozzles where the compressed working fluid mixes with fuel and ignites in a combustion chamber to generate combustion gases having a high temperature and pressure.
  • the combustion gases flow through a transition piece to the turbine and expand in the turbine to produce work. For example, expansion of the combustion gases in the turbine may rotate a shaft connected to a generator to produce electricity.
  • the combustion gases exiting the turbine include varying amounts of nitrogen oxides, carbon monoxide, unburned hydrocarbons, and other undesirable emissions, with the actual amount of each emission dependent on the combustor design and operating parameters. For example, a longer residence time of the fuel-air mixture in the combustion chamber generally increases the nitrogen oxide levels, while a shorter residence time of the fuel-air mixture in the combustion chamber generally increases the carbon monoxide and unburned hydrocarbon levels. Similarly, higher combustion gas temperatures associated with higher power operations generally increase the nitrogen oxide levels, while lower combustion gas temperatures associated with lower fuel-air mixtures and/or turndown operations generally increase the carbon monoxide and unburned hydrocarbon levels.
  • one or more late lean injectors, passages, or tubes may be circumferentially arranged around the combustion chamber downstream from the fuel nozzles.
  • a portion of the compressed working fluid exiting the compressor may be diverted to flow through the injectors to mix with fuel to produce a lean fuel-air mixture.
  • the lean fuel-air mixture may then flow into the combustion chamber where it ignites to raise the combustion gas temperature and increase the thermodynamic efficiency of the combustor.
  • the circumferentially arranged late lean injectors are effective at increasing combustion gas temperatures without producing a corresponding increase undesirable emissions, liquid fuel supplied to the late lean injectors often results in excessive coking in the fuel passages.
  • the circumferential delivery of the lean fuel-air mixture into the combustion chamber may also result in liquid fuel streaming along the inside of the combustion chamber and transition piece, creating localized hot streaks that may reduce the low cycle fatigue limit for these components.
  • a system for supplying liquid and/or gaseous fuel for late lean combustion without producing localized hot streaks along the inside of the combustion chamber and transition piece would be useful.
  • One embodiment of the present invention is a system for supplying fuel to a combustor that includes a combustion chamber and a fuel nozzle that provides fluid communication into the combustion chamber.
  • a plurality of passages circumferentially arranged around the combustion chamber provide fluid communication into the combustion chamber.
  • a liquid fuel plenum provides fluid communication to the plurality of passages.
  • a baffle circumferentially surrounds at least a portion of the liquid fuel plenum inside the plurality of passages and forms a plurality of lobes around the liquid fuel plenum.
  • Another embodiment of the present invention is a system for supplying fuel to a combustor that includes a combustion chamber and a liner that circumferentially surrounds at least a portion of the combustion chamber.
  • a plurality of passages extend through the liner and into the combustion chamber.
  • a liquid fuel plenum extends inside each of the plurality of passages.
  • a baffle circumferentially surrounds at least a portion of the liquid fuel plenum inside the plurality of passages and forms a plurality of lobes around the liquid fuel plenum.
  • a system for supplying fuel to a combustor includes a combustion chamber and a liner that circumferentially surrounds at least a portion of the combustion chamber.
  • a plurality of injectors circumferentially arranged around the combustion chamber provide fluid communication through the liner and into the combustion chamber.
  • a liquid fuel plenum is centrally aligned inside at least some of the plurality of injectors.
  • a baffle circumferentially surrounding at least a portion of the liquid fuel plenum inside the at least some of the plurality of injectors forms a plurality of lobes around the liquid fuel plenum.
  • FIG. 1 is a simplified side cross-section view of an exemplary gas turbine
  • FIG. 2 is a partial perspective and side cross-section view of a portion of the combustion chamber shown in FIG. 1 according to a first embodiment of the present invention
  • FIG. 3 is a side cross-section view of a portion of the combustion chamber shown in FIG. 1 according to a second embodiment of the present invention
  • FIG. 4 is a side cross-section view of the injector shown in FIG. 2 according to a particular embodiment of the present invention.
  • FIG. 5 is a radial plan view of the injector shown in FIG. 4 ;
  • FIG. 6 is a radial plan view of the injector shown in FIG. 4 according to an alternate embodiment.
  • Various embodiments of the present invention include a system for supplying fuel to a combustor.
  • the combustor generally includes a combustion chamber defined at least in part by a liner that circumferentially surrounds at least a portion of the combustion chamber.
  • the system includes one or more passages or injectors circumferentially arranged around the combustion chamber to provide fluid communication into the combustion chamber, and a liquid fuel plenum provides fluid communication to the passages or injectors.
  • a baffle circumferentially surrounds at least a portion of the liquid fuel plenum and forms a plurality of lobes around the liquid fuel plenum.
  • the baffle defines fluid flow passages inside and outside of the baffle, and the lobes mix the fluid flow between the passages to enhance liquid fuel atomization, vaporization, and/or mixing prior to injection into the combustion chamber.
  • FIG. 1 provides a simplified cross-section of an exemplary gas turbine 10 that may incorporate various embodiments of the present invention.
  • the gas turbine 10 may generally include a compressor 12 at the front, one or more combustors 14 radially disposed around the middle, and a turbine 16 at the rear.
  • the compressor 12 and the turbine 16 may share a common rotor 18 connected to a generator 20 to produce electricity.
  • the compressor 12 may be an axial flow compressor in which a working fluid 22 , such as ambient air, enters the compressor 12 and passes through alternating stages of stationary vanes 24 and rotating blades 26 .
  • a compressor casing 28 contains the working fluid 22 as the stationary vanes 24 and rotating blades 26 accelerate and redirect the working fluid 22 to produce a continuous flow of compressed working fluid 22 .
  • the majority of the compressed working fluid 22 flows through a compressor discharge plenum 30 to the combustor 14 .
  • the combustor 14 may be any type of combustor known in the art.
  • a combustor casing 32 may circumferentially surround some or all of the combustor 14 to contain the compressed working fluid 22 flowing from the compressor 12 .
  • One or more fuel nozzles 34 may be radially arranged in an end cover 36 to supply fuel to a combustion chamber 38 downstream from the fuel nozzles 34 .
  • Possible fuels include, for example, one or more of blast furnace gas, coke oven gas, natural gas, vaporized liquefied natural gas (LNG), hydrogen, and propane.
  • the compressed working fluid 22 may flow from the compressor discharge passage 30 along the outside of the combustion chamber 38 before reaching the end cover 36 and reversing direction to flow through the fuel nozzles 34 to mix with the fuel.
  • the mixture of fuel and compressed working fluid 22 flows into the combustion chamber 38 where it ignites to generate combustion gases having a high temperature and pressure.
  • the combustion gases flow through a transition piece 40 to the turbine 16 .
  • the turbine 16 may include alternating stages of stators 42 and rotating buckets 44 .
  • the first stage of stators 42 redirects and focuses the combustion gases onto the first stage of turbine buckets 44 .
  • the combustion gases expand, causing the turbine buckets 44 and rotor 18 to rotate.
  • the combustion gases then flow to the next stage of stators 42 which redirects the combustion gases to the next stage of rotating turbine buckets 44 , and the process repeats for the following stages.
  • the various embodiments described herein include one or more injectors, passages, or tubes 50 circumferentially arranged around the combustion chamber 38 downstream from the fuel nozzles 34 .
  • a portion of the compressed working fluid 22 exiting the compressor 12 may be diverted to flow through the injectors 50 to mix with the same or a different liquid and/or gaseous fuel than is supplied to the fuel nozzles 34 to produce a lean fuel-air mixture.
  • the lean fuel-air mixture may then flow into the combustion chamber 38 where it ignites to raise the combustion gas temperature and increase the thermodynamic efficiency of the combustor 14 .
  • FIG. 2 provides a partial perspective and side cross-section view of a portion of the combustion chamber 38 shown in FIG. 1 according to a first embodiment of the present invention.
  • a liner 52 circumferentially surrounds at least a portion of the combustion chamber 38
  • a flow sleeve 54 circumferentially surrounds at least a portion of the liner 52 to create an annular passage 56 between the liner 52 and the flow sleeve 54 .
  • a portion of the compressed working fluid 22 may flow through the annular passage 56 to remove heat from the liner 52 before reaching the end cover 36 and reversing direction to flow through the fuel nozzles 34 , as previously described with respect to FIG. 1 .
  • the injectors, passages, or tubes 50 are circumferentially arranged around the combustion chamber 38 , liner 52 , and flow sleeve 54 to provide fluid communication through the flow sleeve 54 and liner 52 into the combustion chamber 38 .
  • liquid and/or gaseous fuel may be supplied to the injectors 50 to mix with a portion of the compressed working fluid 22 that flows through the injectors 50 and into the combustion chamber 38 .
  • a liquid fuel plenum 60 may circumferentially surround the combustion chamber 38 , and a portion of the liquid fuel plenum 60 may extend inside one or more of the injectors 50 to provide fluid communication for liquid fuel to flow into the injectors 50 .
  • the liquid fuel plenum 60 may include one or more liquid fuel ports 62 that provide fluid communication for the liquid fuel to flow into the injectors 50 and mix with the compressed working fluid 22 before reaching the combustion chamber 38 .
  • the flow sleeve 54 may include an internal fuel passage 64
  • each injector 50 may include one or more gaseous fuel ports 66 circumferentially arranged around the injector 50 .
  • the gaseous fuel ports 66 may thus provide fluid communication for the gaseous fuel to flow into the injectors 50 and mix with the compressed working fluid 22 before reaching the combustion chamber 38 .
  • the injectors 50 may supply a lean mixture of liquid and/or gaseous fuel for additional combustion to raise the temperature, and thus the efficiency, of the combustor 14 .
  • FIG. 3 provides a side cross-section view of a portion of the combustion chamber 38 shown in FIG. 1 according to a second embodiment of the present invention.
  • an impingement sleeve 68 circumferentially surrounds at least a portion of the transition piece 40 to create an annular passage 70 between the transition piece 40 and the impingement sleeve 68 .
  • the impingement sleeve 68 may include a plurality of apertures 72 that allow a portion of the compressed working fluid 22 to flow through the annular passage 70 to remove heat from the transition piece 40 .
  • the injectors, passages, or tubes 50 are circumferentially arranged around the combustion chamber 38 , transition piece 40 , and impingement sleeve 68 to provide fluid communication through the impingement sleeve 68 and transition piece 40 into the combustion chamber 38 .
  • the liquid fuel plenum 60 may extend through the casing 32 and inside one or more of the injectors 50 to provide fluid communication for liquid fuel to flow into the injectors 50 .
  • a gaseous fuel plenum 74 may similarly extend through the casing 32 to provide fluid communication for the gaseous fuel to flow through gaseous fuel ports 66 circumferentially arranged around the injectors 50 , as previously described with respect to the embodiment shown in FIG. 2 .
  • the liquid and/or gaseous fuel plenums 60 , 74 may supply liquid and/or gaseous fuel through the injectors 50 and into the combustion chamber 38 for additional combustion.
  • FIG. 4 provides a side cross-section view of the injector 50 shown in FIG. 2 according to a particular embodiment of the present invention.
  • the injector 50 may include a passage, tube, or other structure for providing fluid communication through the flow sleeve 54 and liner 52 and into the combustion chamber 38 .
  • a portion of the injector 50 extends inside the combustion chamber 38 to enhance mixing between the liquid and/or gaseous fuel and the compressed working fluid 22 before mixing with the combustion gases flowing through the combustion chamber 38 .
  • the liquid fuel plenum 60 may extend at least partially inside the injector 50 , and the gaseous fuel ports 66 circumferentially arranged around the injector 50 may provide fluid communication for the gaseous fuel to flow from the internal fuel passage 64 in the flow sleeve 54 into the injector 50 .
  • a baffle 80 connected to the injector 50 , liner 52 , and/or the liquid fuel plenum 60 may circumferentially surround at least a portion of the liquid fuel plenum 60 inside the injector 50 .
  • the baffle 80 may define a first fluid passage 82 between the liquid fuel plenum 60 and the baffle 80 and a second fluid passage 84 between the baffle 80 and the injector 50 .
  • the baffle 80 may include a flared or bellmouth opening 86 at the inlet to the injector 50 as shown in FIG. 4 to preferentially divert more of the compressed working fluid 22 into the first fluid passage 82 .
  • FIGS. 5 and 6 provide radial plan views of the injector 50 shown in FIG. 4 as seen from inside the combustion chamber 38 to more clearly illustrate particular features of the baffle 80 according to various embodiments of the present invention.
  • one or more struts 88 may extend between the baffle 80 and the injector 50 , liner 52 , and/or liquid fuel plenum 60 to hold the baffle 80 in place.
  • a portion of the compressed working fluid 22 may flow through the first fluid passage 82 between the liquid fuel plenum 60 and the baffle 80 to mix with the liquid fuel flowing out of the liquid fuel ports 62 .
  • Another portion of the compressed working fluid 22 may also flow through the second fluid passage 84 between the baffle 80 and the injector 50 to mix with the gaseous fuel flowing out of the gaseous fuel ports 66 .
  • the downstream portion of the baffle 80 may include alternating lobes 90 and vertices 92 circumferentially surrounding the liquid fuel plenum 60 and the liquid fuel ports 62 .
  • the liquid fuel ports 62 are radially aligned coincident with the vertices 92 and between adjacent lobes 90 .
  • the liquid fuel ports 62 are radially aligned coincident with the lobes 90 and between adjacent vertices 92 .
  • the alternating lobes 90 and vertices 92 in the baffle 80 push fluid flow through the first fluid passage 82 radially outward while drawing fluid flow through the second fluid passage 84 radially inward.
  • the lobes 90 and vertices 92 in the baffle 80 create shear between the fluid flowing through the first and second fluid passages 82 , 84 to enhance evaporation, atomization, and/or mixing of the liquid fuel with the gaseous fuel and/or compressed working fluid 22 .
  • the various embodiments shown and described with respect to FIGS. 1-6 may provide one or more benefits over existing combustor designs.
  • the lean fuel-air mixture supplied to the combustion chamber 38 may increase the combustion gas temperature to enhance combustor 14 efficiency without producing a corresponding increase in NO X emissions.
  • the various embodiments described herein enable liquid fuel to be supplied through the injectors 50 without creating localized hot streaks along the inside of the combustion chamber 38 and transition piece 40 that may reduce the low cycle fatigue limit for these components.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
US13/457,726 2012-04-27 2012-04-27 System for supplying fuel to a late-lean fuel injector of a combustor Active 2034-09-05 US9200808B2 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US13/457,726 US9200808B2 (en) 2012-04-27 2012-04-27 System for supplying fuel to a late-lean fuel injector of a combustor
EP13165222.4A EP2657611B1 (en) 2012-04-27 2013-04-24 System for supplying fuel to a combustor
JP2013091859A JP6203528B2 (ja) 2012-04-27 2013-04-25 燃焼器への燃料供給システム
CN201310149399.5A CN103375816B (zh) 2012-04-27 2013-04-26 用于将燃料供应到燃烧器的系统
RU2013119328A RU2618765C2 (ru) 2012-04-27 2013-04-26 Система для подачи топлива в камеру сгорания (варианты)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/457,726 US9200808B2 (en) 2012-04-27 2012-04-27 System for supplying fuel to a late-lean fuel injector of a combustor

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US20130283801A1 US20130283801A1 (en) 2013-10-31
US9200808B2 true US9200808B2 (en) 2015-12-01

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US (1) US9200808B2 (enExample)
EP (1) EP2657611B1 (enExample)
JP (1) JP6203528B2 (enExample)
CN (1) CN103375816B (enExample)
RU (1) RU2618765C2 (enExample)

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US20160153662A1 (en) * 2014-11-28 2016-06-02 Snecma Annular deflection wall for a turbomachine combustion chamber injection system providing a wide fuel atomization zone
US10309655B2 (en) * 2014-08-26 2019-06-04 Siemens Energy, Inc. Cooling system for fuel nozzles within combustor in a turbine engine
US20190178498A1 (en) * 2017-12-11 2019-06-13 General Electric Company Axial fuel staging system for gas turbine combustors
US10502426B2 (en) 2017-05-12 2019-12-10 General Electric Company Dual fuel injectors and methods of use in gas turbine combustor
US10690349B2 (en) * 2017-09-01 2020-06-23 General Electric Company Premixing fuel injectors and methods of use in gas turbine combustor
US11022308B2 (en) 2018-05-31 2021-06-01 Honeywell International Inc. Double wall combustors with strain isolated inserts
US11187415B2 (en) * 2017-12-11 2021-11-30 General Electric Company Fuel injection assemblies for axial fuel staging in gas turbine combustors
US20220099297A1 (en) * 2020-09-25 2022-03-31 General Electric Company Fuel injector for a turbomachine
DE102022208339A1 (de) * 2022-08-10 2024-02-15 Rolls-Royce Deutschland Ltd & Co Kg Brennkammeranordnung zum Betrieb mit flüssigem und/oder gasförmigem Kraftstoff, Gasturbinenanordnung und Verfahren
US12188658B1 (en) 2023-07-07 2025-01-07 Ge Infrastructure Technology Llc Fuel injection assembly for a combustor
US12449128B1 (en) 2024-11-27 2025-10-21 Ge Vernova Infrastructure Technology Llc Boss for a fuel injection assembly having cooling circuit and combustor provided therewith
US12467630B2 (en) 2023-07-07 2025-11-11 Ge Vernova Infrastructure Technology Llc Fuel injection assembly having a boss with a serpentine cooling passage

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US8904796B2 (en) * 2011-10-19 2014-12-09 General Electric Company Flashback resistant tubes for late lean injector and method for forming the tubes
US20130111918A1 (en) * 2011-11-07 2013-05-09 General Electric Company Combustor assembly for a gas turbomachine
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CN104870902A (zh) * 2012-12-13 2015-08-26 川崎重工业株式会社 适合多种燃料的燃气轮机燃烧器
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JP2016109309A (ja) * 2014-12-02 2016-06-20 川崎重工業株式会社 ガスタービン用燃焼器、及びガスタービン
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US11029030B2 (en) * 2016-08-03 2021-06-08 Siemens Energy Global GmbH & Co. KG Ducting arrangement with injector assemblies configured to form a shielding flow of air injected into a combustion stage in a gas turbine engine
US20180340689A1 (en) * 2017-05-25 2018-11-29 General Electric Company Low Profile Axially Staged Fuel Injector
US10816203B2 (en) * 2017-12-11 2020-10-27 General Electric Company Thimble assemblies for introducing a cross-flow into a secondary combustion zone
US11933223B2 (en) * 2019-04-18 2024-03-19 Rtx Corporation Integrated additive fuel injectors for attritable engines
KR102164620B1 (ko) * 2019-06-19 2020-10-12 두산중공업 주식회사 연소기 및 이를 포함하는 가스터빈
US11846426B2 (en) 2021-06-24 2023-12-19 General Electric Company Gas turbine combustor having secondary fuel nozzles with plural passages for injecting a diluent and a fuel
CN114909675B (zh) * 2022-04-07 2024-03-01 中国联合重型燃气轮机技术有限公司 用于燃气涡轮机的燃烧室和燃气轮机
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CN115075946B (zh) * 2022-07-01 2024-11-01 星辰萌想科技(北京)有限公司 一种双燃烧部燃气轮机
CN115059544A (zh) * 2022-07-01 2022-09-16 星辰萌想科技(北京)有限公司 一种具有双燃烧部的燃气轮机
US12429224B1 (en) * 2024-05-09 2025-09-30 Ge Infrastructure Technology Llc Axial fuel stage injector with fuel injection in same direction as high-pressure air flow

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RU2618765C2 (ru) 2017-05-11
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EP2657611A2 (en) 2013-10-30
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CN103375816A (zh) 2013-10-30
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US20130283801A1 (en) 2013-10-31
EP2657611A3 (en) 2017-11-22

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